GB950181A - Improvements in and relating to starting control arrangements of gas turbines - Google Patents

Improvements in and relating to starting control arrangements of gas turbines

Info

Publication number
GB950181A
GB950181A GB1672459A GB1672459A GB950181A GB 950181 A GB950181 A GB 950181A GB 1672459 A GB1672459 A GB 1672459A GB 1672459 A GB1672459 A GB 1672459A GB 950181 A GB950181 A GB 950181A
Authority
GB
United Kingdom
Prior art keywords
valve
motor
turbine
pressure
bleed
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB1672459A
Inventor
Waheeb Rizk
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
English Electric Co Ltd
Original Assignee
English Electric Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by English Electric Co Ltd filed Critical English Electric Co Ltd
Priority to GB1672459A priority Critical patent/GB950181A/en
Priority claimed from FR826969A external-priority patent/FR1256860A/en
Publication of GB950181A publication Critical patent/GB950181A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26Starting; Ignition
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26Starting; Ignition
    • F02C7/268Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/27Fluid drives
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S388/00Electricity: motor control systems
    • Y10S388/923Specific feedback condition or device
    • Y10S388/929Fluid/granular material flow rate, pressure, or level

Abstract

950,181. Starting prime-movers. ENGLISH ELECTRIC CO. Ltd May 13, 1960 [May 15, 1959], No. 16724/59. Heading H2H. [Also in Divisions Fl and G3] During starting of a gas turbine the energy supplied to an electric starter motor 1 is increased, and so also is the turbine fuel supply, by fluid pressure responsive devices connected to an hydraulic pressure generator 2 coupled to the starter motor. Rising pressure in the line 22 increasingly closes an obturator 17 in a bleed unit connected to a separate control fluid line 27; this second control fluid acts on the piston 51 of a spring-loaded fuel valve 101, the valve progressively opening as the obturator closes. The starting motor is accelerated by the sequential short circuiting of resistors 10, 11, 12 by pressure-operated switches 4, 5, 6. The motor may be D.C., the resistors being in the supply circuit, or A.C., when the resistors are in the rotor circuit. Another pressure switch 31 initiates a timing device 37 controlling an igniter 36 and its gas supply valve 33, and a further switch 32 opens a second fuel supply valve 39. At self-sustaining speed another pressure switch 14 disconnects the motor and, in the arrangement shown, closes a valve 29 to cut off the control fluid bleed unit. The clutch 26 is also disconnected. At this speed a time controlled cam starts to rotate to progressively close a second bleed 54, so that the fuel supply is further increased to run the turbine up to governing speed. Another bleed valve 53 is controlled by devices (not shown) sensitive to turbine temperatures or pressures, fuel to air ratio or the like. If the motor 1 fails to stop, a final pressure switch 56 shuts down the turbine. In an alternative arrangement the clutch 26 is between the motor 1 and the pressure generator drive so that this continues to be driven by the turbine. In this case the bleed unit is kept in operation up to governing speed, and so obviates cam-controlled bleed 54. The pressure generator 2 may be a positive displacement or a centrifugal pump, with a temperature sensitive valve 21 or other means to compensate for varying viscosity of the fluid, or it may be a total pressure head device (Fig. 2, not shown). This control fluid may be part of the fuel or lubricating oil system.
GB1672459A 1959-05-15 1959-05-15 Improvements in and relating to starting control arrangements of gas turbines Expired GB950181A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1672459A GB950181A (en) 1959-05-15 1959-05-15 Improvements in and relating to starting control arrangements of gas turbines

Applications Claiming Priority (7)

Application Number Priority Date Filing Date Title
NL251582D NL251582A (en) 1959-05-15
NL113963D NL113963C (en) 1959-05-15
GB1672459A GB950181A (en) 1959-05-15 1959-05-15 Improvements in and relating to starting control arrangements of gas turbines
US27632A US3057155A (en) 1959-05-15 1960-05-09 Starting control arrangements of gas turbines
CH545760A CH381473A (en) 1959-05-15 1960-05-12 starting gear for a gas turbine group
FR826969A FR1256860A (en) 1959-05-15 1960-05-12 starting controller for gas turbines
DE19601426251 DE1426251A1 (en) 1959-05-15 1960-05-16 Start control apparatus for gas turbines

Publications (1)

Publication Number Publication Date
GB950181A true GB950181A (en) 1964-02-19

Family

ID=10082510

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1672459A Expired GB950181A (en) 1959-05-15 1959-05-15 Improvements in and relating to starting control arrangements of gas turbines

Country Status (5)

Country Link
US (1) US3057155A (en)
CH (1) CH381473A (en)
DE (1) DE1426251A1 (en)
GB (1) GB950181A (en)
NL (2) NL251582A (en)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3793825A (en) * 1972-01-27 1974-02-26 Ford Motor Co Time delay gas turbine starting system with fuel pressure and flame sensing circuitry
US3991558A (en) * 1975-12-01 1976-11-16 General Motors Corporation Turbine engine starting fuel control
US4783755A (en) * 1986-02-11 1988-11-08 Jet Electronics & Technology, Inc. Interval timer circuit
US9200592B2 (en) * 2011-06-28 2015-12-01 United Technologies Corporation Mechanism for turbine engine start from low spool
JP2013170524A (en) * 2012-02-21 2013-09-02 Mitsubishi Heavy Ind Ltd Gas turbine starting and stopping device
US10443507B2 (en) 2016-02-12 2019-10-15 United Technologies Corporation Gas turbine engine bowed rotor avoidance system
US10125636B2 (en) 2016-02-12 2018-11-13 United Technologies Corporation Bowed rotor prevention system using waste heat
US10436064B2 (en) 2016-02-12 2019-10-08 United Technologies Corporation Bowed rotor start response damping system
US9664070B1 (en) 2016-02-12 2017-05-30 United Technologies Corporation Bowed rotor prevention system
US10508567B2 (en) 2016-02-12 2019-12-17 United Technologies Corporation Auxiliary drive bowed rotor prevention system for a gas turbine engine through an engine accessory
US10443505B2 (en) 2016-02-12 2019-10-15 United Technologies Corporation Bowed rotor start mitigation in a gas turbine engine
US10539079B2 (en) 2016-02-12 2020-01-21 United Technologies Corporation Bowed rotor start mitigation in a gas turbine engine using aircraft-derived parameters
US10040577B2 (en) 2016-02-12 2018-08-07 United Technologies Corporation Modified start sequence of a gas turbine engine
US10508601B2 (en) 2016-02-12 2019-12-17 United Technologies Corporation Auxiliary drive bowed rotor prevention system for a gas turbine engine
US10174678B2 (en) 2016-02-12 2019-01-08 United Technologies Corporation Bowed rotor start using direct temperature measurement
US10125691B2 (en) 2016-02-12 2018-11-13 United Technologies Corporation Bowed rotor start using a variable position starter valve
EP3211184A1 (en) 2016-02-29 2017-08-30 United Technologies Corporation Bowed rotor prevention system and associated method of bowed rotor prevention
US10358936B2 (en) 2016-07-05 2019-07-23 United Technologies Corporation Bowed rotor sensor system
US10221774B2 (en) 2016-07-21 2019-03-05 United Technologies Corporation Speed control during motoring of a gas turbine engine
US10618666B2 (en) 2016-07-21 2020-04-14 United Technologies Corporation Pre-start motoring synchronization for multiple engines
US10384791B2 (en) 2016-07-21 2019-08-20 United Technologies Corporation Cross engine coordination during gas turbine engine motoring
EP3273006B1 (en) 2016-07-21 2019-07-03 United Technologies Corporation Alternating starter use during multi-engine motoring
US10443543B2 (en) 2016-11-04 2019-10-15 United Technologies Corporation High compressor build clearance reduction

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US765030A (en) * 1903-11-10 1904-07-12 Edward Talcott Moore Combined starter and regulator for electric motors.
US1343212A (en) * 1917-03-08 1920-06-15 Westinghouse Electric & Mfg Co Starting device for electric motors
US1807280A (en) * 1927-04-02 1931-05-26 Charles E Carpenter Electric motor speed controller
US2262195A (en) * 1936-12-10 1941-11-11 Bbc Brown Boveri & Cie Hot gas producing and consuming plant
US2452298A (en) * 1944-10-20 1948-10-26 Chrysler Corp Starter
GB614341A (en) * 1946-07-10 1948-12-14 Gordon Henry Clifford Rawlinso Improvements in or relating to liquid fuel systems for gas turbines
US2632294A (en) * 1948-04-19 1953-03-24 John J Wall Fuel supplying means for jet engines
US2559006A (en) * 1948-04-28 1951-07-03 Power Jets Res & Dev Ltd Rotary starting means for rotary engines with cartridge chamber and surplus gas releasing means
US2617253A (en) * 1950-09-23 1952-11-11 Gen Electric Safety control system for cooling a gas turbine power plant on shutdown
US2808702A (en) * 1951-03-13 1957-10-08 Garrett Corp Gas turbine pneumatic governor fuel supply control
GB731698A (en) * 1952-10-07 1955-06-15 Raymond Ernest Wigg Improvements in and relating to control devices for internal combustion engines
US2680202A (en) * 1952-10-17 1954-06-01 Electrom Neuilly Sur Seine Current supply and starting method and unit, notably for aircraft propulsed by turbomachines or reciprocating engines
US2862355A (en) * 1955-05-26 1958-12-02 Gen Motors Corp Turbine starting fuel system

Also Published As

Publication number Publication date
CH381473A (en) 1964-08-31
NL251582A (en)
US3057155A (en) 1962-10-09
NL113963C (en)
DE1426251A1 (en) 1969-05-08

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